US10808718B2 - Fan blade composite segments - Google Patents

Fan blade composite segments Download PDF

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Publication number
US10808718B2
US10808718B2 US15/032,900 US201415032900A US10808718B2 US 10808718 B2 US10808718 B2 US 10808718B2 US 201415032900 A US201415032900 A US 201415032900A US 10808718 B2 US10808718 B2 US 10808718B2
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Prior art keywords
pocket
blade
blade body
composite segments
leading edge
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US20160252104A1 (en
Inventor
Kwan Hui
Michael A. Weisse
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RTX Corp
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Raytheon Technologies Corp
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Publication of US20160252104A1 publication Critical patent/US20160252104A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y02T50/672—

Definitions

  • the present disclosure relates to fan blades, and more particularly to fan blade assemblies for gas turbine engines, for example.
  • a turbo fan engine for an aircraft has a turbine that drives fan blades to draw air into the engine as the turbine rotates.
  • the fan blades are exposed to the atmosphere in front of the engine and have the potential for an impact with birds or other foreign objects that may be drawn into the engine.
  • fan blades can be made out of titanium or aluminum.
  • Traditional titanium fan blades are relatively strong, but they are heavy and expensive to manufacture.
  • impact with a bird or other foreign object, as described above, can damage the blade and cover and lead to premature failure.
  • a fan blade includes a blade body, a composite segment and a cover.
  • the blade body extends from a blade root to an opposed blade tip along a longitudinal axis.
  • the blade body defines a leading edge and a trailing edge, a first airfoil surface extending from the leading edge to the trailing edge, and a pocket defined between the leading edge, the trailing edge, the blade root and the blade tip.
  • the pocket has a bottom surface that opposes the first airfoil surface across the blade body.
  • the composite segment is disposed in the pocket.
  • the cover is mounted to the composite segment and to the blade body to form a second airfoil surface opposed to the first airfoil surface.
  • a composite segment can be adhered to the bottom surface of the pocket and/or adhered to the cover to resist forces acting on the cover in order to secure the cover to the blade body.
  • the pocket of the blade body can be at least partially filled with lightweight filler material.
  • the cover can include a composite material, and/or titanium.
  • the blade body can include titanium.
  • a clearance can be defined between the composite segment and each of a leading edge side of the pocket and a trailing edge side of the pocket and/or a clearance can be defined between the composite segment and a pocket perimeter. The clearance can be configured to provide flexibility to the cover when forces are acting on the cover decreasing the likelihood that the cover will disbond from the blade body.
  • blade body can include a recessed lip defined around its perimeter. An interior surface of the cover can be adhered to the blade body on the recessed lip. The recessed lip can be configured to allow the cover to be mounted flush with the blade body.
  • the composite segment can be a first composite segment.
  • the fan blade can include at least one additional composite segment to form a plurality of composite segments.
  • the plurality of composite segments can be adhered to the bottom surface of the pocket, and/or can be adhered to the cover to resist forces, as described above.
  • a clearance can be defined between the plurality of composite segments and each of a leading edge side of the pocket and a trailing edge side of the pocket, and/or a clearance can be defined between the plurality of composite segments and a pocket perimeter.
  • FIG. 1 is a is a perspective exploded view of an exemplary embodiment of a fan blade constructed in accordance with the present disclosure, showing a plurality of composite segments between the blade body and the cover;
  • FIG. 2 is a cross-sectional side-elevation view the fan blade shown in FIG. 1 , showing the first and second airfoil surfaces and the composite segments;
  • FIG. 3 is a is partial perspective view the fan blade shown in FIG. 1 , showing the composite segments adhered to the bottom surface of the pocket, and the clearance between the composite segments and the pocket perimeter.
  • FIG. 1 a partial view of an exemplary embodiment of the fan assembly in accordance with the disclosure is shown in FIG. 1 and is designated generally by reference character 100 .
  • FIGS. 2-3 Other embodiments of fan blades in accordance with the disclosure, or aspects thereof, are provided in FIGS. 2-3 , as will be described.
  • a fan blade 100 includes a blade body 102 , composite segments 104 form a plurality of composite segments 108 , and a cover 106 .
  • Blade body 102 extends from a blade root 103 to an opposed blade tip 105 along a longitudinal axis A.
  • Blade body 102 defines a leading edge 107 and a trailing edge 109 , a first airfoil surface 111 , shown in FIG. 2 , extending from leading edge 107 to trailing edge 109 , and a pocket 112 defined between leading edge 107 , trailing edge 109 , blade root 103 and blade tip 105 .
  • Pocket 112 has a bottom surface 110 that opposes the first airfoil surface across blade body 102 .
  • Composite segments 104 are disposed in pocket 112 . While shown and described herein as having one pocket 112 , those skilled in the art will readily appreciate that blade body 102 can have multiple pockets 112 .
  • cover 106 is mounted to composite segments 104 and to blade body 102 to form a second airfoil surface 114 opposed to first airfoil surface 111 .
  • Blade body 102 includes a recessed lip 116 defined around its perimeter.
  • An interior surface 119 of cover 106 is adhered to blade body 102 on recessed lip 116 .
  • Recessed lip 116 is configured to allow cover 106 to be mounted flush with blade body 102 .
  • cover 106 can be a composite material and/or titanium, and that blade body 102 can include titanium.
  • pocket 112 shown in FIG. 1
  • of blade body 102 can be at least partially filled with lightweight filler material which may be any type of numerous fillers.
  • a plurality of composite segments 108 is adhered to the bottom surface of pocket 112 .
  • Composite segments 108 are adhered to cover 106 , as shown in FIG. 2 , to resist forces acting on cover 106 in order to secure cover 106 to blade body 102 .
  • a clearance 117 is defined between composite segments 108 and each of a leading edge side 113 of pocket 112 and a trailing edge side 115 of pocket 112 .
  • Clearance 117 is also defined between composite segments 108 and a pocket perimeter 118 .
  • composite segments 108 are disjointed from one another and from the pocket perimeter 118 of blade 102 . This lends flexibility while providing enhanced adhesive surface area.
  • clearance 117 can be a variety of sizes as suitable for a given application.
  • clearance 117 can be configured to provide flexibility to cover 106 when forces are acting on cover 106 decreasing the likelihood that cover 106 will disbond from blade body 102 .
  • composite segments 104 can be manufactured in a variety of ways as suitable for a given application, for example, machined chopped fiber or molded unitape. Further, those skilled in the art will also readily appreciate that composite segments 104 have sufficient tensile strength such that the composite segments 104 will not crack into pieces in case of impact, for example, a bird strike. While described and shown herein as fan blade composite segments 108 , those skilled in the art will readily appreciate that composite segments 108 can be used in a variety of turbo-machine blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Architecture (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A fan blade includes a blade body, a composite segment and a cover. The blade body extends from a blade root to an opposed blade tip along a longitudinal axis. The blade body defines a leading edge and a trailing edge. A first airfoil surface extends from the leading edge to the trailing edge. A pocket is defined between the leading edge, the trailing edge, the blade root and the blade tip. The pocket has a bottom surface that opposes the first airfoil surface across the blade body. The composite segment is disposed in the pocket. The cover is mounted to the composite segment and to the blade body to form a second airfoil surface opposed to the first airfoil surface.

Description

RELATED APPLICATIONS
This application claims the benefit of and priority to U.S. Provisional Patent Application No. 61/897,685 filed Oct. 30, 2013, the contents of which are incorporated herein by reference in their entirety.
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present disclosure relates to fan blades, and more particularly to fan blade assemblies for gas turbine engines, for example.
2. Description of Related Art
Traditionally, a turbo fan engine for an aircraft has a turbine that drives fan blades to draw air into the engine as the turbine rotates. The fan blades are exposed to the atmosphere in front of the engine and have the potential for an impact with birds or other foreign objects that may be drawn into the engine.
It is known that fan blades can be made out of titanium or aluminum. Traditional titanium fan blades are relatively strong, but they are heavy and expensive to manufacture. In order to reduce weight without sacrificing strength, it is known to machine out pockets from a titanium fan blade and adhere a cover to the fan blade. However, impact with a bird or other foreign object, as described above, can damage the blade and cover and lead to premature failure.
Such conventional methods and systems have generally been considered satisfactory for their intended purpose. However, there is still a need in the art for blade assemblies that allow for improved impact resistance. The present disclosure provides a solution for these problems.
SUMMARY OF THE INVENTION
A fan blade includes a blade body, a composite segment and a cover. The blade body extends from a blade root to an opposed blade tip along a longitudinal axis. The blade body defines a leading edge and a trailing edge, a first airfoil surface extending from the leading edge to the trailing edge, and a pocket defined between the leading edge, the trailing edge, the blade root and the blade tip. The pocket has a bottom surface that opposes the first airfoil surface across the blade body. The composite segment is disposed in the pocket. The cover is mounted to the composite segment and to the blade body to form a second airfoil surface opposed to the first airfoil surface.
It is contemplated that a composite segment can be adhered to the bottom surface of the pocket and/or adhered to the cover to resist forces acting on the cover in order to secure the cover to the blade body. Further, the pocket of the blade body can be at least partially filled with lightweight filler material. The cover can include a composite material, and/or titanium. The blade body can include titanium. In addition, a clearance can be defined between the composite segment and each of a leading edge side of the pocket and a trailing edge side of the pocket and/or a clearance can be defined between the composite segment and a pocket perimeter. The clearance can be configured to provide flexibility to the cover when forces are acting on the cover decreasing the likelihood that the cover will disbond from the blade body. It is further contemplated that blade body can include a recessed lip defined around its perimeter. An interior surface of the cover can be adhered to the blade body on the recessed lip. The recessed lip can be configured to allow the cover to be mounted flush with the blade body.
In certain embodiments, the composite segment can be a first composite segment. The fan blade can include at least one additional composite segment to form a plurality of composite segments. The plurality of composite segments can be adhered to the bottom surface of the pocket, and/or can be adhered to the cover to resist forces, as described above. Further, a clearance can be defined between the plurality of composite segments and each of a leading edge side of the pocket and a trailing edge side of the pocket, and/or a clearance can be defined between the plurality of composite segments and a pocket perimeter. In addition, there can be at least one clearance separation between each of the plurality of composite segments and the others.
These and other features of the systems and methods of the subject disclosure will become more readily apparent to those skilled in the art from the following detailed description of the preferred embodiments taken in conjunction with the drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
So that those skilled in the art to which the subject disclosure appertains will readily understand how to make and use the devices and methods of the subject disclosure without undue experimentation, preferred embodiments thereof will be described in detail herein below with reference to certain figures, wherein:
FIG. 1 is a is a perspective exploded view of an exemplary embodiment of a fan blade constructed in accordance with the present disclosure, showing a plurality of composite segments between the blade body and the cover;
FIG. 2 is a cross-sectional side-elevation view the fan blade shown in FIG. 1, showing the first and second airfoil surfaces and the composite segments; and
FIG. 3 is a is partial perspective view the fan blade shown in FIG. 1, showing the composite segments adhered to the bottom surface of the pocket, and the clearance between the composite segments and the pocket perimeter.
 DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an exemplary embodiment of the fan assembly in accordance with the disclosure is shown in FIG. 1 and is designated generally by reference character 100. Other embodiments of fan blades in accordance with the disclosure, or aspects thereof, are provided in FIGS. 2-3, as will be described.
As shown in at least FIGS. 1 and 2, a fan blade 100 includes a blade body 102, composite segments 104 form a plurality of composite segments 108, and a cover 106. Blade body 102 extends from a blade root 103 to an opposed blade tip 105 along a longitudinal axis A. Blade body 102 defines a leading edge 107 and a trailing edge 109, a first airfoil surface 111, shown in FIG. 2, extending from leading edge 107 to trailing edge 109, and a pocket 112 defined between leading edge 107, trailing edge 109, blade root 103 and blade tip 105. Pocket 112 has a bottom surface 110 that opposes the first airfoil surface across blade body 102. Composite segments 104 are disposed in pocket 112. While shown and described herein as having one pocket 112, those skilled in the art will readily appreciate that blade body 102 can have multiple pockets 112.
Now with reference to FIG. 2, cover 106 is mounted to composite segments 104 and to blade body 102 to form a second airfoil surface 114 opposed to first airfoil surface 111. Blade body 102 includes a recessed lip 116 defined around its perimeter. An interior surface 119 of cover 106 is adhered to blade body 102 on recessed lip 116. Recessed lip 116 is configured to allow cover 106 to be mounted flush with blade body 102. It is contemplated that cover 106 can be a composite material and/or titanium, and that blade body 102 can include titanium. Those skilled in the art will readily appreciate that, in addition to composite segments 104, pocket 112, shown in FIG. 1, of blade body 102 can be at least partially filled with lightweight filler material which may be any type of numerous fillers.
As shown in at least FIGS. 1 and 3, a plurality of composite segments 108 is adhered to the bottom surface of pocket 112. Composite segments 108 are adhered to cover 106, as shown in FIG. 2, to resist forces acting on cover 106 in order to secure cover 106 to blade body 102. A clearance 117 is defined between composite segments 108 and each of a leading edge side 113 of pocket 112 and a trailing edge side 115 of pocket 112. Clearance 117 is also defined between composite segments 108 and a pocket perimeter 118. In addition, there is a clearance 117 defined between each composite segment 104 separately there from one another. In other words, composite segments 108 are disjointed from one another and from the pocket perimeter 118 of blade 102. This lends flexibility while providing enhanced adhesive surface area. Those skilled in the art will readily appreciate that clearance 117 can be a variety of sizes as suitable for a given application.
Those skilled in the art will readily appreciate that clearance 117 can be configured to provide flexibility to cover 106 when forces are acting on cover 106 decreasing the likelihood that cover 106 will disbond from blade body 102. It is contemplated that composite segments 104 can be manufactured in a variety of ways as suitable for a given application, for example, machined chopped fiber or molded unitape. Further, those skilled in the art will also readily appreciate that composite segments 104 have sufficient tensile strength such that the composite segments 104 will not crack into pieces in case of impact, for example, a bird strike. While described and shown herein as fan blade composite segments 108, those skilled in the art will readily appreciate that composite segments 108 can be used in a variety of turbo-machine blades.
The methods and systems of the present disclosure, as described above and shown in the drawings, provide for fan blade assemblies with superior properties including improved impact resistance. While the apparatus and methods of the subject disclosure have been shown and described with reference to preferred embodiments, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the spirit and scope of the subject disclosure.

Claims (6)

What is claimed is:
1. A fan blade, comprising:
a blade body extending from a blade root to a blade tip along a longitudinal axis, wherein the blade body defines a leading edge and a trailing edge, a first airfoil surface extending from the leading edge to the trailing edge, the blade body being formed from a first material;
a pocket defined in the blade body and located between the leading edge, the trailing edge, the blade root and the blade tip;
a plurality of composite segments disposed in the pocket and separately adhered to a bottom surface of the pocket, the plurality of composite segments being formed from a second material, the second material being different from the first material;
a clearance defined between each of the plurality of composite segments and between the plurality of composite segments and each of a leading edge side of the pocket, a pocket perimeter and a trailing edge side of the pocket such that the plurality of composite segments are disjointed from one another; and
a separate cover separately mounted to the plurality of composite segments and to the blade body to form a second airfoil surface, wherein the clearance between each of the plurality of composite segments and between the plurality of composite segments and each of a leading edge side of the pocket, a pocket perimeter and a trailing edge side of the pocket is configured to provide flexibility to the separate cover.
2. A fan blade as recited in claim 1, wherein the bottom surface opposes the first airfoil surface across the blade body.
3. A fan blade as recited in claim 1, wherein the plurality of composite segments are adhered to the separate cover to resist forces acting on the separate cover in order to secure the separate cover to the blade body.
4. A fan blade as recited in claim 1, wherein the blade body includes a recessed lip defined around a perimeter of the pocket.
5. A fan blade as recited in claim 4, wherein an interior surface of the separate cover is adhered to the blade body on the recessed lip, and the recessed lip is configured to allow the separate cover to be mounted flush with the blade body.
6. A fan blade as recited in claim 1, wherein the pocket of the blade body is at least partially filled with lightweight filler material.
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US11639685B1 (en) * 2021-11-29 2023-05-02 General Electric Company Blades including integrated damping structures and methods of forming the same
US20240200458A1 (en) * 2022-12-20 2024-06-20 Rtx Corporation Hollow airfoil construction using cover subassembly

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EP2896789B1 (en) * 2014-01-16 2018-03-07 United Technologies Corporation Fan blade with variable thickness composite cover
GB2553331A (en) * 2016-09-02 2018-03-07 Rolls Royce Plc Gas turbine engine
US11131314B2 (en) 2016-09-14 2021-09-28 Raytheon Technologies Corporation Fan blade with structural spar and integrated leading edge
US11168566B2 (en) * 2016-12-05 2021-11-09 MTU Aero Engines AG Turbine blade comprising a cavity with wall surface discontinuities and process for the production thereof
US10822969B2 (en) * 2018-10-18 2020-11-03 Raytheon Technologies Corporation Hybrid airfoil for gas turbine engines
US11248477B2 (en) 2019-08-02 2022-02-15 Raytheon Technologies Corporation Hybridized airfoil for a gas turbine engine
FR3100471B1 (en) * 2019-09-10 2022-12-09 Safran Aircraft Engines Preform for composite blade

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